Abstract:

In this work, an eddy breakup model for chemical reactions is implemented to an existing multi-block Navier-Stokes solver, which is then used to solve the flow past a supersonic long-range base-bleed projectile. The new scheme is validated by simulating an axisymmetric bluff-body stabilized flame, which has been measured in a wind tunnel and simulated numerically by other work groups.

Comparison of the numerical results for the projectile shows the importance of the chemistry modelling for accurate numerical predictions. The final combustion of the fuel-rich propellant simulated in this work makes a dramatic difference in the predicted aerodynamic drag of the projectile. The drag reduction due to base bleed is more than doubled when the chemical reactions are accounted for, and the drag prediction based on the simulations including chemical reactions is excellent.